GOE 406 AIRFOIL (goe406-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 406 AIRFOIL (goe406-il) Reynolds number: 200,000 Max Cl/Cd: 75.62 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe406-il-200000.txt Download as CSV file: xf-goe406-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 406 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2644 0.11946 0.11597 -0.0341 1.0000 0.0381
-10.000 -0.2664 0.11749 0.11406 -0.0331 1.0000 0.0387
-9.750 -0.2731 0.11608 0.11273 -0.0313 1.0000 0.0391
-9.500 -0.2622 0.11282 0.10949 -0.0346 0.9974 0.0402
-9.250 -0.2449 0.10889 0.10554 -0.0421 0.9928 0.0414
-9.000 -0.2352 0.10456 0.10122 -0.0525 0.9856 0.0421
-8.750 -0.2076 0.10001 0.09665 -0.0529 0.9839 0.0427
-8.500 -0.1871 0.09629 0.09293 -0.0561 0.9778 0.0435
-8.250 -0.1656 0.09249 0.08911 -0.0610 0.9729 0.0446
-8.000 -0.1483 0.08880 0.08543 -0.0657 0.9647 0.0459
-7.750 -0.1307 0.08462 0.08123 -0.0754 0.9575 0.0480
-7.500 -0.1280 0.08071 0.07723 -0.0873 0.9363 0.0486
-7.250 -0.1089 0.07612 0.07268 -0.0875 0.9320 0.0491
-7.000 -0.0845 0.07259 0.06914 -0.0887 0.9290 0.0499
-6.750 -0.0686 0.06957 0.06610 -0.0906 0.9188 0.0507
-6.500 -0.0426 0.06590 0.06238 -0.0957 0.9137 0.0532
-6.250 -0.0195 0.06188 0.05791 -0.1079 0.8995 0.0565
-6.000 0.0024 0.05744 0.05358 -0.1087 0.8945 0.0572
-5.750 0.0244 0.05457 0.05070 -0.1097 0.8870 0.0581
-5.500 0.0553 0.05149 0.04754 -0.1133 0.8820 0.0600
-5.250 0.0753 0.04893 0.04485 -0.1148 0.8712 0.0626
-5.000 0.0970 0.04590 0.04133 -0.1173 0.8612 0.0663
-4.750 0.1201 0.04300 0.03845 -0.1183 0.8529 0.0674
-4.500 0.1398 0.04104 0.03641 -0.1182 0.8434 0.0690
-4.250 0.1635 0.03914 0.03433 -0.1187 0.8347 0.0724
-4.000 0.1758 0.03765 0.03237 -0.1163 0.8246 0.0776
-3.750 0.1983 0.03535 0.03008 -0.1166 0.8172 0.0793
-3.500 0.2121 0.03405 0.02872 -0.1145 0.8076 0.0817
-3.000 0.2454 0.03135 0.02548 -0.1104 0.7900 0.0913
-2.750 0.2673 0.02976 0.02382 -0.1099 0.7827 0.0939
-2.500 0.2822 0.02888 0.02285 -0.1074 0.7746 0.0989
-2.250 0.3002 0.02765 0.02132 -0.1053 0.7679 0.1064
-2.000 0.3199 0.02646 0.02009 -0.1040 0.7616 0.1105
-1.750 0.3358 0.02578 0.01916 -0.1013 0.7543 0.1218
-1.500 0.3591 0.02450 0.01785 -0.1007 0.7485 0.1275
-1.250 0.3749 0.02368 0.01693 -0.0983 0.7413 0.1407
-1.000 0.3940 0.02281 0.01598 -0.0966 0.7341 0.1583
-0.750 0.4159 0.02196 0.01505 -0.0955 0.7280 0.1773
-0.500 0.4549 0.01918 0.01119 -0.0928 0.7214 0.0718
-0.250 0.4843 0.01847 0.01007 -0.0919 0.7149 0.0656
0.000 0.5105 0.01756 0.00910 -0.0913 0.7079 0.0648
0.250 0.5369 0.01689 0.00835 -0.0907 0.6999 0.0646
0.500 0.5649 0.01643 0.00779 -0.0903 0.6927 0.0660
0.750 0.5886 0.01581 0.00724 -0.0893 0.6836 0.0684
1.000 0.6159 0.01538 0.00678 -0.0889 0.6761 0.0697
1.250 0.6367 0.01507 0.00650 -0.0872 0.6665 0.0717
1.500 0.6608 0.01478 0.00619 -0.0861 0.6580 0.0747
1.750 0.6810 0.01447 0.00589 -0.0842 0.6477 0.0792
2.000 0.7015 0.01428 0.00570 -0.0824 0.6370 0.0899
2.250 0.9165 0.01248 0.00562 -0.1240 0.6083 1.0000
2.500 0.9362 0.01257 0.00562 -0.1221 0.5920 1.0000
2.750 0.9548 0.01270 0.00565 -0.1200 0.5726 1.0000
3.000 0.9725 0.01286 0.00569 -0.1178 0.5504 1.0000
3.250 0.9893 0.01310 0.00576 -0.1154 0.5261 1.0000
3.500 1.0053 0.01340 0.00588 -0.1128 0.5003 1.0000
3.750 1.0213 0.01377 0.00605 -0.1104 0.4783 1.0000
4.000 1.0384 0.01416 0.00629 -0.1082 0.4594 1.0000
4.250 1.0562 0.01458 0.00656 -0.1063 0.4443 1.0000
4.500 1.0750 0.01499 0.00684 -0.1045 0.4321 1.0000
4.750 1.0948 0.01537 0.00716 -0.1030 0.4219 1.0000
5.250 1.1359 0.01617 0.00782 -0.1004 0.4056 1.0000
5.500 1.1576 0.01659 0.00815 -0.0993 0.3990 1.0000
5.750 1.1791 0.01699 0.00853 -0.0982 0.3928 1.0000
6.000 1.2003 0.01736 0.00892 -0.0971 0.3869 1.0000
6.250 1.2240 0.01782 0.00929 -0.0965 0.3818 1.0000
6.500 1.2460 0.01823 0.00973 -0.0956 0.3772 1.0000
6.750 1.2677 0.01862 0.01017 -0.0945 0.3728 1.0000
7.000 1.2906 0.01903 0.01059 -0.0938 0.3687 1.0000
7.250 1.3171 0.01955 0.01104 -0.0939 0.3650 1.0000
7.500 1.3389 0.02000 0.01157 -0.0929 0.3614 1.0000
7.750 1.3575 0.02039 0.01206 -0.0913 0.3568 1.0000
8.000 1.3774 0.02079 0.01246 -0.0901 0.3514 1.0000
8.250 1.3994 0.02130 0.01294 -0.0893 0.3459 1.0000
8.500 1.4128 0.02165 0.01344 -0.0867 0.3405 1.0000
8.750 1.4304 0.02204 0.01384 -0.0850 0.3352 1.0000
9.000 1.4533 0.02257 0.01433 -0.0845 0.3300 1.0000
9.250 1.4639 0.02294 0.01487 -0.0814 0.3254 1.0000
9.500 1.4767 0.02329 0.01528 -0.0788 0.3198 1.0000
9.750 1.4985 0.02380 0.01572 -0.0781 0.3141 1.0000
10.000 1.5029 0.02413 0.01625 -0.0739 0.3100 1.0000
10.250 1.5085 0.02444 0.01666 -0.0699 0.3048 1.0000
10.500 1.5210 0.02481 0.01701 -0.0674 0.2994 1.0000
10.750 1.5244 0.02523 0.01757 -0.0633 0.2940 1.0000
11.000 1.5278 0.02563 0.01810 -0.0594 0.2882 1.0000
11.250 1.5376 0.02608 0.01853 -0.0567 0.2823 1.0000
11.500 1.5371 0.02665 0.01930 -0.0525 0.2761 1.0000
11.750 1.5379 0.02726 0.01999 -0.0487 0.2687 1.0000
12.000 1.5387 0.02804 0.02090 -0.0452 0.2605 1.0000
12.250 1.5374 0.02899 0.02190 -0.0417 0.2510 1.0000
12.500 1.5359 0.03015 0.02322 -0.0386 0.2383 1.0000
12.750 1.5308 0.03176 0.02488 -0.0356 0.2196 1.0000
13.000 1.5209 0.03405 0.02712 -0.0327 0.1841 1.0000
13.250 1.4964 0.03786 0.03060 -0.0295 0.1380 1.0000
13.500 1.4704 0.04224 0.03477 -0.0267 0.1093 1.0000
13.750 1.4494 0.04650 0.03894 -0.0247 0.0892 1.0000
14.000 1.4318 0.05069 0.04310 -0.0232 0.0754 1.0000
14.250 1.4159 0.05494 0.04736 -0.0222 0.0685 1.0000
14.500 1.4036 0.05899 0.05149 -0.0216 0.0648 1.0000
14.750 1.3871 0.06377 0.05633 -0.0213 0.0617 1.0000
15.000 1.3721 0.06857 0.06122 -0.0213 0.0597 1.0000
15.250 1.3609 0.07304 0.06583 -0.0215 0.0578 1.0000
15.500 1.3482 0.07784 0.07075 -0.0219 0.0560 1.0000
15.750 1.3336 0.08301 0.07601 -0.0225 0.0543 1.0000
16.000 1.3215 0.08787 0.08092 -0.0232 0.0532 1.0000
16.250 1.3095 0.09260 0.08567 -0.0237 0.0518 1.0000
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